Variable volume combustor with pre-nozzle fuel injection system

Patent metadata

Field	Value
Publication number	US-9435539-B2
Application number	US-201313760091-A
Country	US
Kind code	B2
Filing date	Feb 6, 2013
Priority date	Feb 6, 2013
Publication date	Sep 6, 2016
Grant date	Sep 6, 2016

Abstract

The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system.

First claim

We claim:

1. A combustor for use with a gas turbine engine, comprising:
a liner;
a cap assembly;
a seal in between the liner and the cap assembly;
a head end with a head end volume;
a combustion zone with a combustion zone volume;
a plurality of fuel nozzles positioned within the cap assembly;
a pre-nozzle fuel injection system supporting the plurality of fuel nozzles, wherein the pre-nozzle fuel injection system separates the head end from the combustion zone; and
a linear actuator to maneuver the plurality of fuel nozzles and the pre-nozzle fuel injection system, such that the head end volume is increased as the combustion zone volume is decreased.

2. The combustor of claim 1 , wherein the plurality of fuel nozzles comprises a plurality of micro-mixer fuel nozzles.

3. The combustor of claim 1 , further comprising a common fuel tube in communication with the pre-nozzle fuel injection system.

4. The combustor of claim 1 , wherein the pre-nozzle fuel injection system comprises a fuel nozzle manifold.

5. The combustor of claim 4 , wherein the fuel nozzle manifold comprises a center hub.

6. The combustor of claim 1 , wherein the pre-nozzle fuel injection system comprises a plurality of support struts supporting the plurality of fuel nozzles.

7. The combustor of claim 6 , wherein the plurality of support struts comprises a substantially aerodynamically contoured shape.

8. The combustor of claim 6 , wherein the plurality of support struts is positioned upstream of the plurality of fuel nozzles.

9. The combustor of claim 6 , wherein the plurality of support struts comprises a plurality of fuel injections holes.

10. The combustor of claim 9 , wherein the plurality of support struts comprises a first side wall and a second side wall and wherein the plurality of fuel injection holes is positioned thereon.

11. The combustor of claim 9 , wherein a pre-nozzle fuel flow passes through the plurality of fuel injection holes.

12. The combustor of claim 11 , wherein the pre-nozzle flow comprises about twenty percent or less of a flow of fuel to the plurality of fuel nozzles.

13. The combustor of claim 1 , wherein the linear actuator comprises a drive rod in communication with the pre-nozzle fuel injection system.

14. A method of operating a combustor in a gas turbine engine, the combustor comprising a liner, a cap assembly, and a seal in between the liner and the cap assembly, the method comprising:
supporting a plurality of fuel nozzles about a plurality of support struts, the plurality of fuel nozzles positioned within the cap assembly;
flowing a flow of fuel through the plurality of support struts to the plurality of fuel nozzles;
actuating the plurality of fuel nozzles from a first position to a second position, such that a head end volume of the combustor is increased as a combustion zone volume of the combustor is decreased;
diverting a pre-nozzle flow of fuel from the plurality of support struts;
flowing a flow of air through the plurality of support struts; and
mixing the flow of air and the pre-nozzle flow of fuel upstream of the plurality of fuel nozzles.

15. A combustor for use with a gas turbine engine, comprising:
a liner;
a cap assembly;
a seal in between the liner and the cap assembly;
a head end with a head end volume;
a combustion zone with a combustion zone volume;
a plurality of micro-mixer fuel nozzles positioned within the cap assembly;
a plurality of support struts supporting the plurality of micro-mixer fuel nozzles;
the plurality of support struts comprising a plurality of fuel injections holes thereon; and
a linear actuator to maneuver the plurality of micro-mixer fuel nozzles and the plurality of support struts, such that the head end volume is increased as the combustion zone volume is decreased.

16. The combustor of claim 15 , wherein the plurality of support struts comprises a substantially aerodynamically contoured shape.

17. The combustor of claim 15 , wherein the plurality of support struts is positioned upstream of the plurality of fuel nozzles.

18. The combustor of claim 15 , wherein the plurality of support struts comprises a first side wall and a second side wall and wherein the plurality of fuel injection holes is positioned thereon.

19. The combustor of claim 15 , wherein a pre-nozzle fuel flow passes through the plurality of fuel injection holes.

Assignees

• Gen Electric

Inventors

• Keener Christopher Paul
• Johnson Thomas Edward
• Mcconnaughhay Johnie Franklin
• Ostebee Heath Michael

Classifications

• F23C5/06

  Provision for adjustment of burner position during operation · CPC title

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title